Aircraft structure with hinge rib assembly

Abstract

An aircraft structure comprising; a rear spar, an upper cover which is attached to the rear spar and overhangs to its rear; a lower cover which is attached to the rear spar and overhangs to its rear, a hinge rib assembly comprising: a first hinge rib arm attached to a first one of the covers; and a second hinge rib arm connected to the first hinge rib arm and attached to a second one of the covers; and an aerodynamic control element pivotally mounted to the hinge rib assembly. The first and second hinge rib arms are separate parts. This provides the ability to disassemble the hinge rib in-situ for repair or maintenance purposes; the ability to install or remove the hinge rib without having to move it inboard along the structure; reduced material wastage during manufacture; and the ability to install one or more elongate lines which extend in a span-wise direction along the aircraft structure.

1. A method of installing an aerodynamic control element on an aircraft structure, the aircraft structure comprising a rear spar, an upper cover which is attached to the rear spar and overhangs to its rear, and a lower cover which is attached to the rear spar and overhangs to its rear, the method comprising in any order:
 a. fastening a first hinge rib arm directly to a first one of the covers; 
 b. assembling a hinge rib by connecting the first hinge rib arm to a second hinge rib arm; 
 c. fastening the second hinge rib arm directly to a second one of the covers; and 
 d. pivotally mounting the aerodynamic control element to the hinge rib. 
 
     
     
       2. The method of  claim 1  further comprising:
 e. before assembling a hinge rib by connecting the first hinge rib arm to a second hinge rib arm or fastening the second hinge rib arm to a second one of the covers, installing one or more elongate lines which extend in a span-wise direction along the aircraft structure. 
 
     
     
       3. The method of  claim 1 , further comprising: fastening a first hinge rib arm to a first one of the covers or fastening the second hinge rib arm to a second one of the covers before assembling a hinge rib by connecting the first hinge rib arm to a second hinge rib arm. 
     
     
       4. An aircraft structure comprising;
 a rear spar, 
 an upper cover which is attached to the rear spar and overhangs to its rear; 
 a lower cover which is attached to the rear spar and overhangs to its rear, 
 a hinge rib assembly comprising: 
 a first hinge rib arm fastened directly to a first one of the covers; and 
 a second hinge rib arm connected to the first hinge rib arm and fastened directly to a second one of the covers; and 
 an aerodynamic control element pivotally mounted to the hinge rib assembly; 
 wherein the first and second hinge rib arms are separate parts. 
 
     
     
       5. The structure of  claim 4  wherein the first hinge rib arm is pivotally connected to the second hinge rib arm. 
     
     
       6. The structure of  claim 5  wherein the second hinge rib arm is pivotally connected to the second one of the covers. 
     
     
       7. The structure of  claim 4  wherein the first hinge rib arm has a greater maximum cross-sectional area than the second hinge rib arm. 
     
     
       8. The structure of  claim 4  wherein the first and second hinge rib arms are also each attached to the rear spar. 
     
     
       9. The structure of  claim 4  wherein the upper and lower covers converge towards each other aft of the rear spar. 
     
     
       10. The structure of  claim 4  further comprising one or more elongate lines passing through a space between the hinge rib arms in a span-wise direction. 
     
     
       11. The structure of  claim 4  wherein one of the covers comprises one or more ramps along which the thickness of the cover decreases. 
     
     
       12. A method of disassembling the structure of  claim 4 , the method comprising disconnecting the second hinge rib arm from the first hinge rib arm or from the second one of the covers whilst keeping the first hinge rib arm attached to the first one of the covers. 
     
     
       13. The method of  claim 12  further comprising: detaching the first or second hinge rib arm from the respective cover thereof after the second hinge rib arm has been disconnected. 
     
     
       14. The method of  claim 12  further comprising removing or repairing an elongate line passing through a space between the hinge rib arms in a span-wise direction.